Patents Examined by Dwayne J. White
  • Patent number: 9829004
    Abstract: Provided is a turbofan including a shroud, a main plate, and a plurality of blades. A main plate-side shoulder surface portion is curved so as to be distanced from the rotational center axis while approaching the blade trailing edge as the main plate-side shoulder surface portion is distanced from a main plate-side blade tip portion, and has a convexoconcave shape including a blade tip section and the main plate-side blade tip portion. An inner peripheral-side leading edge section includes the inner peripheral-side blade leading edge section main plate-side portion and an inner peripheral-side blade leading edge section tip-side portion including curves that protrude rearward in the rotational direction.
    Type: Grant
    Filed: October 15, 2013
    Date of Patent: November 28, 2017
    Assignee: Mitsubishi Electric Corporation
    Inventors: Takashi Ikeda, Masahiko Takagi, Makoto Kurihara
  • Patent number: 9828860
    Abstract: A compressor blade of a gas turbine includes an airfoil made of a fiber-reinforced plastic and a leading-edge element connected to said airfoil. The leading-edge element includes two partial elements, which are fabricated as separate elements and connected to one another, with the leading-edge element being connected to the airfoil essentially using the clamping effect of the two partial elements.
    Type: Grant
    Filed: July 30, 2013
    Date of Patent: November 28, 2017
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Karl Schreiber
  • Patent number: 9828876
    Abstract: A fan case for use in a gas turbine engine of an aircraft includes an outer shroud and a liner extending along the outer shroud. The fan case provides a protective band that blocks fan blades from being thrown out of the fan case in case of a blade-off event in which a fan blade is released during operation of the gas turbine engine.
    Type: Grant
    Filed: April 27, 2015
    Date of Patent: November 28, 2017
    Assignee: Rolls-Royce Corporation
    Inventor: Matthew J. Kappes
  • Patent number: 9822800
    Abstract: The present disclosure relates to a support frame for a ventilation device for cooling a fluid which passes through a cooling circuit of a motor vehicle. The support frame comprises an opening, which is designed to receive a propeller, and a central support, which is positioned in a center of the opening. The central support is formed to receive a motor which activates the propeller, so as to generate a ventilation flow. The central support is attached through the opening to the support frame by retention arms. The retention arms extend according to a curved form, between the central support and a periphery of the opening.
    Type: Grant
    Filed: December 19, 2014
    Date of Patent: November 21, 2017
    Assignee: VALEO SYSTEMS THERMIQUES
    Inventors: Herve Pegues, Vincent Zuba
  • Patent number: 9822653
    Abstract: Embodiments of the present disclosure provide a cooling structure for a stationary blade. The cooling structure can include: an airfoil having a cooling circuit therein; an endwall coupled to a radial end of the airfoil; a chamber positioned within the endwall for receiving a cooling fluid from the cooling circuit, wherein the cooling fluid absorbs heat from the endwall, and a temperature of the cooling fluid in an upstream region is lower than a temperature of the cooling fluid in a downstream region; a first passage within the endwall fluidly connecting the upstream region of the chamber to a wheel space positioned between the endwall and the turbine wheel; and a second passage within the endwall fluidly connecting the downstream region of the chamber to the wheel space.
    Type: Grant
    Filed: July 16, 2015
    Date of Patent: November 21, 2017
    Assignee: General Electric Company
    Inventors: Christopher Donald Porter, Christopher Lee Golden
  • Patent number: 9816389
    Abstract: In accordance with an exemplary embodiment, a turbine rotor blade is provided for a turbine section of an engine. The turbine rotor blade includes a platform and an airfoil extending from the platform into a mainstream gas path of the turbine section. The airfoil includes a first side wall; a second side wall joined to the first side wall at a leading edge and a trailing edge; a tip cap extending between the first side wall and the second side wall; a first parapet wall extending from the first side wall; a first parapet wall cavity formed at least partially within the first parapet wall; and a first cooling hole extending between the first parapet wall cavity and a first surface of the first parapet wall such that cooling air flows through the first parapet wall cavity, through the first cooling hole, and out of the first parapet wall.
    Type: Grant
    Filed: October 16, 2013
    Date of Patent: November 14, 2017
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Malak Fouad Malak, Mark C. Morris, David Waldman
  • Patent number: 9816528
    Abstract: A fluid-flow machine includes at least one rotor having a rotary element with a plurality of rotor blades arranged on the rotary element, and a circumferential casing having a central axis and surrounding the rotor. The circumferential casing or a part connected thereto has an annular space surface on the inside, which delimits a flow duct of the fluid-flow machine radially outwards. The annular space surface has a structuring at least in one area adjoining a rotor on the circumferential side. At least one structuring of the annular space surface has, relative to the central axis of the circumferential casing, a circumferentially asymmetrical design.
    Type: Grant
    Filed: April 20, 2012
    Date of Patent: November 14, 2017
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Erik Johann
  • Patent number: 9816488
    Abstract: A rotor turning system includes a fixture plate configured for attachment to a gearbox, a locking mechanism configured for attachment to the fixture plate, and a reaction fixture configured for attachment to the locking mechanism. The rotor turning system is configured to permit rotation of the rotor only when rotational torque is applied to the locking mechanism, and this rotation is in only one rotational direction.
    Type: Grant
    Filed: October 31, 2013
    Date of Patent: November 14, 2017
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Raymond Francis Rose, Jr., Jeffrey Eric Bergman, Brent Hamilton Holloway, Drake Joseph Viscome
  • Patent number: 9816489
    Abstract: Towers for wind turbines are provided. In one embodiment, a tower includes a hollow shell defining an interior, the hollow shell extending generally along a longitudinal axis. The tower further includes a platform disposed in the interior and connected to the shell. The platform includes a first plate fixedly connected to the shell. The platform further includes a second plate movably connected to the first plate such that relative movement of the first plate and second plate is permitted in a plane generally transverse to the longitudinal axis.
    Type: Grant
    Filed: July 30, 2013
    Date of Patent: November 14, 2017
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Raghunandan Chickballapur Venkatakrishnappa, Umesh B. Shingne
  • Patent number: 9816393
    Abstract: The disclosure pertains to a turbine with a gas turbine blade and a rotor heat shield for separating a space region through which hot working medium flows from a space region inside a rotor arrangement of the turbine. The rotor heat shield includes a platform which forms an axial heat shield section and which is arranged substantially parallel to the surface of a rotor and a radial heat shield section at the upstream end of the axial heat shield section, which is extending in a direction away from the surface of the axial heat shield section towards the hot gas. Further the turbine comprises a blade rear cavity which is delimited by the downstream end of the platform and/or the downstream end of the blade foot, the radial heat shield section. The disclosure further refers to a gas turbine blade and a rotor heat shield designed for such a turbine.
    Type: Grant
    Filed: July 21, 2014
    Date of Patent: November 14, 2017
    Assignee: ANSALDO ENERGIA IP UK LIMITED
    Inventors: Carlos Simon-Delgado, Christoph Didion, Stefan Biedermann, Beat Von Arx, Thomas Zierer
  • Patent number: 9816387
    Abstract: An airfoil fairing shell for a gas turbine engine includes an airfoil section between an outer vane endwall and an inner vane endwall, at least one of the outer vane endwall and the inner vane endwall including a radial attachment face, a suction side tangential attachment face, a pressure side tangential attachment face, and an axial attachment face.
    Type: Grant
    Filed: September 1, 2015
    Date of Patent: November 14, 2017
    Assignee: United Technologies Corporation
    Inventors: Jesse M Carr, Bryan P Dube
  • Patent number: 9810075
    Abstract: A damper seal received in a cavity of a turbine blade includes a central body with two ends and a two sides. A portion extends from each end, one side has a faceted edge, and a projection extends from the other side to receive a lug of the turbine blade to align the damper seal relative to the turbine blade.
    Type: Grant
    Filed: March 20, 2015
    Date of Patent: November 7, 2017
    Assignee: United Technologies Corporation
    Inventors: Kyle C. Lana, John E. Paul
  • Patent number: 9810226
    Abstract: The axial compressor has a two-stage guide vane cascade at the discharge-side end of the rotor. The guide vanes of the second stage of the cascade are staggered in the circumferential direction in relation to the guide vanes of the first stage in such a way that vortex streamers created by the guide vanes of the first stage cannot impinge upon the guide vanes of the second stage.
    Type: Grant
    Filed: June 14, 2013
    Date of Patent: November 7, 2017
    Assignee: ANSALDO ENERGIA IP UK LIMITED
    Inventors: Marco Micheli, Wolfgang Kappis, Luis Federico Puerta
  • Patent number: 9810087
    Abstract: A sealing structure for a gas turbine engine includes a rotor that has a rim with slots and a cooling passage. The rotor is rotatable about an axis. First and second blades are arranged in the slots and respectively including first and second shelves facing one another within a pocket that is in fluid communication with the cooling passage. The first and second shelves form an opening. A reversible seal is arranged within the pocket and has a body that is configured for operative association with the first and second blades in any of four orientations to seal the opening in a second condition. The seal includes first and second protrusions respectively extending from first and second faces opposing one another. The first protrusions supported on the rim in a first condition.
    Type: Grant
    Filed: June 24, 2015
    Date of Patent: November 7, 2017
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Christopher Corcoran, Daniel A. Snyder
  • Patent number: 9803491
    Abstract: A blade outer air seal (BOAS) for a gas turbine engine, according to an exemplary aspect of the present disclosure includes, among other things a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion and a shiplap structure that at least partially overlaps at least a portion of at least one of the leading edge portion and the trailing edge portion.
    Type: Grant
    Filed: December 31, 2012
    Date of Patent: October 31, 2017
    Assignee: United Technologies Corporation
    Inventors: Brian Ellis Clouse, David F. Cloud, Donna Clough
  • Patent number: 9803621
    Abstract: The present invention relates to methods, apparatus and computer program products for controlling a wind turbine that comprises a nacelle and one or more turbine blades to reduce or prevent edgewise vibrations building up on the one or more turbine blades. It is identified 202 whether the nacelle is unable to yaw to an upwind position and initiating a corrective action 203 to prevent edgewise vibrations building up on the one or more turbine blades if the nacelle is unable to yaw to an upwind position.
    Type: Grant
    Filed: June 6, 2013
    Date of Patent: October 31, 2017
    Assignee: VESTAS WIND SYSTEMS A/S
    Inventors: Kenneth Tougaard Simonsen, Paw Rosenvard, David Steele
  • Patent number: 9797404
    Abstract: A ventilation assembly having a main housing that can be pre-installed in a wall or ceiling aperture. A fan assembly can be inserted through the aperture and releasably mounted within the main housing. The fan assembly can be removed from the main housing and replaced without removing the main housing from the wall or ceiling. An accessory component can be releasably mounted to the fan assembly either through the aperture when the fan assembly is mounted or prior to installation of the fan assembly.
    Type: Grant
    Filed: November 5, 2014
    Date of Patent: October 24, 2017
    Assignee: BROAN-NUTONE LLC
    Inventors: Daniel L. Karst, Benjamin Thorpe Puffer, Brent Elliott Coffey
  • Patent number: 9797266
    Abstract: A closer for an attachment orifice of an OGV in a turbine engine, the vane having a blade fixed to a root provided with attachment orifices, the closer including a cup adapted to be fixed in the attachment orifice of an OGV; a cylindrical shaped plug engaging in the cup, the plug including an upper face inclined relative to the ground plane of the plug; a guide adapted to position the plug on the cup by rotation into a working position, in which the upper face of the plug coincides with the surface level of the vane root; a blocking system to block the plug in the working position.
    Type: Grant
    Filed: June 2, 2015
    Date of Patent: October 24, 2017
    Assignee: SNECMA
    Inventors: Kaƫlig Merwen Orieux, Thierry Georges Paul Papin
  • Patent number: 9797261
    Abstract: A gas turbine engine component, especially an aerofoil-sectioned nozzle guide vane (NGV), having at least one internal cooling chamber for passage of cooling air, the chamber including leading edge portion and one inlet portion via which cooling air may enter the chamber from feed source, wherein the component includes a partitioning element, e.g. curved or scoop-shaped partitioning plate or wall, provided in the chamber inlet portion and defining within the inlet portion a sub-chamber adjacent the leading edge portion, and wherein partitioning element is configured so the cooling air velocity in the sub-chamber is less than the cooling air velocity in the remainder of inlet portion. The reduced velocity of the cooling air in the sub-chamber adjacent the leading edge serves to increase pressure therein, thereby maintaining desired backflow pressure margin between the feed pressure of the cooling air delivered to the showerhead holes and the gas-path from the combustor.
    Type: Grant
    Filed: September 4, 2015
    Date of Patent: October 24, 2017
    Assignee: ROLLS-ROYCE plc
    Inventors: Ian Tibbott, Peter Thomas Ireland, Anthony John Rawlinson, Irene Cresci
  • Patent number: 9797262
    Abstract: A vane cluster includes a split damped outer shroud and an inner shroud spaced from the split damped outer shroud with a multiple of stator vane airfoils that extend between the split damped outer shroud and the inner shroud.
    Type: Grant
    Filed: May 23, 2014
    Date of Patent: October 24, 2017
    Assignee: United Technologies Corporation
    Inventors: Carl S. Richardson, Mark J. Rogers, Jonathan J. Earl, Kenneth E. Carman, Richard K. Hayford